基于伴随方法的单级低速压气机气动设计优化

doi:10.7527/S1000-6893.2019.23368

飞行器气动外形数值优化与设计专栏

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基于伴随方法的单级低速压气机气动设计优化

罗佳奇¹, 杨婧²

1. 浙江大学航空航天学院, 杭州 310027;
2. 德州农工大学机械工程系, College Station TX 77843

收稿日期:2019-08-12 修回日期:2019-09-17 出版日期:2020-05-15 发布日期:2019-10-10
通讯作者: 罗佳奇 E-mail:jiaqil@zju.edu.cn
基金资助:
国家自然科学基金（51676003，51976183）；中央高校基本科研业务费专项资金（2019QNA4058）

Aerodynamic design optimization of a single low-speed compressor stage by an adjoint method

LUO Jiaqi¹, YANG Jing²

1. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China;
2. Department of Mechanical Engineering, Texas A & M University, College Station, TX 77843, United States

Received:2019-08-12 Revised:2019-09-17 Online:2020-05-15 Published:2019-10-10
Supported by:
National Natural Science Foundation of China (51676003, 51976183); the Fundamental Research Funds for the Central Universities of China (2019QNA4058)

摘要/Abstract

摘要： 采用梯度方法对某型4.5级压气机最后级进行气动设计优化研究，梯度由连续伴随方法计算确定，多排伴随方程采用伴随掺混面模型进行数值求解。首先，采用基于经验修正的初步设计方法设计带进口导叶的4.5级低速、低压缩比压气机的原始气动外形。之后，在压气机近失速工况对最后级静子叶片进行伴随气动设计优化，通过优化叶型和安装角降低流动损失，目标函数定义为加权求和形式的熵增和流量偏差，优化中对流量进行约束。最后，开展基于伴随方法的多工况气动设计优化研究，改善两个不同转速条件下最后级的气动性能。优化结果表明，基于伴随方法的多排气动设计优化可以通过改变叶片气动外形提升多排全工况气动性能。

关键词: 气动设计优化, 伴随方法, 多排, 多工况, 掺混面, 流动分离, 压气机

Abstract: The paper presents an aerodynamic shape optimization of the last stage of a 4.5-stage com-pressor by a gradient-based optimization method that adopts the continuous adjoint approach. An adjoint mixing-plane formulation is used to compute the adjoint solutions for multi-stage turbomachines. Firstly, a conventional preliminary design method with empirical correlations are used to produce a base design of a 4.5-stage low-speed and low compression ratio compressor with an inlet guide vane. Then the last stage is redesigned by the adjoint method to reduce the flow losses at the operation condition near stall through modifying the aerodynamic shape and stagger angle of the stator blade. The cost function is defined as a weighted sum of entropy production and the deviation from a given mass flow rate, enforcing the constraint on mass flow rate. Finally, a multi-point design optimization approach by using the adjoint method is employed to improve the performance of the last stage at two different operation conditions. The optimization show that the adjoint-based multi-stage design can improve the aerodynamic performance of a multi-stage compressor by profile modifications.

Key words: aerodynamic design optimization, adjoint method, multi-stage, multi-point, mixing-plane, flow separation, compressor

中图分类号:

V231.3
O354

罗佳奇, 杨婧. 基于伴随方法的单级低速压气机气动设计优化[J]. 航空学报, 2020, 41(5): 623368-623368.

LUO Jiaqi, YANG Jing. Aerodynamic design optimization of a single low-speed compressor stage by an adjoint method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(5): 623368-623368.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于伴随方法的单级低速压气机气动设计优化

Aerodynamic design optimization of a single low-speed compressor stage by an adjoint method

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